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Two full scale crash safety tests of transport aircraft are being conducted to study take-off and landing accidents wherein speeds and loads do not exceed survivable limits. The wings and fuselage are being extensively instrumented to measure loads, accelerations, and fuel pressures. Secondary experiments are also being carried out on board. The data will be used to improve impact protection and to reduce the possibility of fire after impact. A general discussion of the results of the first test is presented.

The opinions expressed in this paper are those of the authors, and do not necessarily represent the opinions of the Federal Aviation Agency or FAA Aviation Research and Development Service. This paper discusses the development of concepts and components for an aircraft crash-resistant fuel system. There is presented the results of programmed study and dynamic test accomplishments from which the crashworthy design and specification criteria were established for crash-resistant cell and safety valve Military Specifications. Also given is a description of the first aircraft crash-resistant fuel cell installation, complete with safety valves and frangible break away components.